CN103363067A - Compact gearbox for ram air turbine oil management - Google Patents

Compact gearbox for ram air turbine oil management Download PDF

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Publication number
CN103363067A
CN103363067A CN2013101014721A CN201310101472A CN103363067A CN 103363067 A CN103363067 A CN 103363067A CN 2013101014721 A CN2013101014721 A CN 2013101014721A CN 201310101472 A CN201310101472 A CN 201310101472A CN 103363067 A CN103363067 A CN 103363067A
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CN
China
Prior art keywords
main body
housing main
ram air
air turbine
end portion
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Granted
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CN2013101014721A
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Chinese (zh)
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CN103363067B (en
Inventor
D.E.拉斯
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Hamilton Sundstrand Corp
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Hamilton Sundstrand Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0434—Features relating to lubrication or cooling or heating relating to lubrication supply, e.g. pumps ; Pressure control
    • F16H57/0443—Features relating to lubrication or cooling or heating relating to lubrication supply, e.g. pumps ; Pressure control for supply of lubricant during tilt or high acceleration, e.g. problems related to the tilt or extreme acceleration of the transmission casing and the supply of lubricant under these conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/045—Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case
    • F16H57/0452—Oil pans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/048—Type of gearings to be lubricated, cooled or heated
    • F16H57/0493—Gearings with spur or bevel gears
    • F16H57/0495—Gearings with spur or bevel gears with fixed gear ratio
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B64D41/007—Ram air turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/21—Elements
    • Y10T74/2186—Gear casings

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Details Of Gearings (AREA)

Abstract

The present invention relates to a compact gearbox for ram air turbine oil management. Concretely, a ram air turbine gearbox housing includes a housing body that has a first flange that defines a first plane and a second flange that defines a second plane that is transverse to the first plane. The housing body extends around an axis and has a first axial end and an opposite, second axial end that are each open to an internal cavity of the housing body. The housing body includes a radially-enlarged section at least partially defining an oil sump within the internal cavity of the housing body.

Description

The compact gear that is used for the ram air turbine oil management
Technical field
Disclosure relate generally to is used to aircraft that the ram air turbine of urgent or additional power is provided.More specifically, the disclosure relates to the gear-box of ram air turbine.
Background technique
Ram air turbine generally includes the turbo machine that connects to drive generator by gear-box.Ram air turbine is used for by extracting power and produce urgent or additional power at aircraft from the air stream along the aircraft outside during flying.When ram air turbine did not use, it was stored in the aircraft.During urgent or additional power, ram air turbine is deployed into operating position from stowed position when needs, and it provides the gap between turbo machine and the aircraft.
The size of the ram air turbine of given aircraft is constrained to preliminary dimension envelope scope (envelope) usually.In addition, have the certain operations constraint, its require when ram air turbine is in stowed position the oil in the gear-box not with Gear Contact.When the ram air turbine of the correct work of design, size and operability constraint have caused sizable challenge.
Summary of the invention
A kind of ram air turbine gearbox-case according to an aspect of the present disclosure comprises housing main body, described housing main body has the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane.Described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, and described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately.Described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part.
A kind of ram air turbine gear-box according to an aspect of the present disclosure comprises housing main body, described housing main body has the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane.Described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, and described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately.Described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part.At least one gear is installed in the described housing main body.
A kind of ram air turbine according to an aspect of the present disclosure comprises generator section, turbo machine section and the gear-box that can move between expanded position and stowed position, described gear-box is connected to described turbo machine section, so that described turbo machine section can operate to drive described generator section by described gear-box.Described gear-box comprises housing main body, and described housing main body has the first flange and the second flange, described the first flange limit the first plane, and described the second flange limit the second plane, described the second flat transverse is in described the first plane.Described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, and described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately.Described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part.
Lid according to a kind of gear-box for ram air turbine of an aspect of the present disclosure comprises circumferential body, and described circumferential body is extended between the first axial side and the second axial side around central opening and about the central axis of described opening.Described circumferential body comprises antelabium, and described antelabium extends to free terminal to limit axial antelabium size from described the first axial side.Described axial antelabium size is about around the circumferential position of described central axis and change.
A kind of method that gear-box is installed on the ram air turbine according to an aspect of the present disclosure comprises: gear-box is provided, and described gear-box comprises such as the described housing main body of above non-limiting example; Described housing main body is fixed to the turbo machine section; And described the second flange is fixed in pillar and the generator section at least one.
Description of drawings
Those skilled in the art will understand various feature and advantage of the present disclosure from following detailed description.The accompanying drawing of this detailed description can briefly introduce as follows.
Fig. 1 shows exemplary aircraft and ram air turbine.
Fig. 2 A shows the perspective view of the gear-box of ram air turbine.
Fig. 2 B shows another perspective view of the gear-box of ram air turbine.
Fig. 2 C shows the sectional view of the gear-box of ram air turbine.
Fig. 3 A shows the perspective view of the housing main body of gear-box.
Fig. 3 B shows the sectional view of the housing main body of Fig. 3 A.
Fig. 4 A shows the sectional view of the gear-box of the ram air turbine that is in stowed position.
Fig. 4 B shows the sectional view of the gear-box of the ram air turbine that is in expanded position.
Fig. 5 shows the lid of the gear-box of ram air turbine.
Embodiment
Fig. 1 shows exemplary ram air turbine 20, and it is illustrated the stowed position (schematically showing) that is in the aircraft 22.The fuselage 24(that ram air turbine 20 is installed to aircraft 22 usually in a known way also schematically shows).Generally speaking, ram air turbine 20 comprises generator section 26, has turbo machine section 28 and the gear-box 30 of turbine bucket 28a, and gear-box 30 is connected to turbo machine section 28 so that turbo machine section 28 can operate to drive generator section 26 by gear-box 30.
When ram air turbine 20 did not use, ram air turbine 20 was stored in the aircraft 22.During urgent or additional power, ram air turbine 20 is deployed into the operating position of expansion shown in line 32 when needs, and the operating position of this expansion is in the air stream of the outside of aircraft 22.Air stream drives turbo machine section 28, and this makes turbine shaft 29 rotations.Turbine shaft 29 connects with live axle 31 by gear-box 30.Live axle is connected into and drives generator section 26.In this example, live axle also is connected into and drives oil hydraulic pump 34.Will be understood that the layout of ram air turbine 20 shown in being not limited to, and instruction disclosed herein can be applicable to other ram air turbines and arranges.
Following description is with reference to Fig. 2 A and 2B, Fig. 2 C and Fig. 3 A and 3B, Fig. 2 A and 2B show the different perspective view of gear-box 30, Fig. 2 C shows the sectional view of gear-box 30, and Fig. 3 A and 3B show respectively the perspective view of housing main body 40 of gear-box 30 and the sectional view of housing main body 40.Housing main body 40 holds at least one gear train 42(Fig. 4 A and 4B usually), at least one gear train 42 is in the inner chamber 44 of housing main body 40.Housing main body 40 has the first flange 46 and the second flange 48, the first flanges 46 limit first plane 46a(Fig. 3 B), the second flange 48 limits the second plane 48a, the second plane 48a transverse to the first plane 46a or with the first plane 46a at angle.As shown in Figure 1, gear-box 30 is fixed to turbo machine section 28 and the second flange 48 is fixed to generator section 26 by pillar 50.Gear-box 30 is installed to turbo machine section 28 by two bearings in the gear-box 30, these two bearings turbine shafts.
Housing main body 40 extends around axis A, and axis A also is the spin axis of turbine bucket 28a.About axis A, housing main body 40 comprises that the first axial end portion 52 and relative the second axial end portion 54, the first axial end portions 52 and the second axial end portion 54 open into the inner chamber 44 in the housing main body 40 separately.Housing main body 40 also comprises and radially amplifies section 40a, radially amplifies the oil groove 56 in the inner chamber 44 that section 40a limits housing main body 40 at least in part.That is to say that radially amplifying section 40a is hollow and restriction internal channel 40b, internal channel 40b is used for the oil of the housing main body 40 of storage gear-box 30.
Housing main body 40 is asymmetrical about radially amplifying section 40a, only partly circumferentially extends around axis A so that radially amplify section 40a.Therefore, being limited at the raceway groove 40b that radially amplifies in the section 40a also only partly circumferentially extends around axis A.The part of raceway groove 40a is in the bottom of gear-box 30 when at stowed position, and is used for storing or holding the oil of oil groove 56.
Housing main body 40 also comprises with the radial depressions section 40c(that radially amplifies section 40a direct neighbor sees Fig. 2 B).Radial depressions section 40c is limited to positive feature (positive feature) the 40d(Fig. 3 A that extends in the oil groove 56).Radial depressions section 40c also serves as rib, to strengthen housing main body 40.Positive feature 40d limits the outstanding wall of oil groove 56 at least in part.Therefore, the size of the positive feature 40d in the inner chamber 44 of the size Control housing main body 40 of the recess of radial depressions section 40c.
The size of positive feature 40d is adjustable to control the expansion volume size of oil groove 56 and control with respect to the innage degree of gear train 42.Expect that minimum oil volume cools off gear train 42 and bearing, and the innage degree is important for oilgear group 42 and allows gear train 42 with oiling agent spilling all the other places to gear-box 30.The radial depressions section 40d of less can increase the volume of oil groove 56, and relatively large radial depressions section 40d can reduce the volume of oil groove 56.Consider the dimension constraint of ram air turbine, radial depressions section 40d and radially amplify section 40a thus make it possible to that housing main body 40 is designed to have the designated volume development size of oil groove 56 and remain axially compact to be engaged in the required size envelope scope.In one example, oil groove 56 has about 5 cubic inches/82 cubic centimetres volume size.Yet the size that will be understood that the size of radial depressions section 40d and radially amplify section 40a can change to adjust the volume size of oil groove 56 as required.
Housing main body 40 also comprises oily filling channel 60(Fig. 3 A), be used for filling oil groove 56 so that the operation of gear-box 30 with oil.Entrance 62(Fig. 2 A that oil filling channel 60 is located in the outside of housing main body 40) and between the outlet 64 at oil groove 56 places extend.Also be provided with drain passage 66 near the bottom of oil groove 56 in order to remove or change oil in the gear-box 30, viewing window 68 provides the visual confirmation for oil level (Fig. 2 A).
Shown in Fig. 4 A and 4B, oily filling channel 60 is positioned at expanded position, so that when ram air turbine 20 is in stowed position (Fig. 4 A), the oil volume in the oil groove 56 is filled oily filling channel 60 in the situation of Contact Tooth wheels 42 not.By contrast, if oily filling channel is in the another location that is different from oil groove 56 places, the oil that then is loaded into gear-box 30 may surpass for fear of the desired predetermined maximum oil mass of gear of oil contact stowed position.That is to say, oily filling channel 60 is positioned at groove 56 places has prevented from will the oil mass larger than necessary amount packing in the gear-box 30 that is in stowed position, to satisfy this requirement.Shown in Fig. 4 B, when being pivoted to expanded position, ram air turbine 20 (sees the line 32 of Fig. 1), exist enough oil masses to come Contact Tooth wheels 42.Generally speaking, when ram air turbine 20 was in stowed position, oil (it has the viscosity of increase in when cooling usually) was held not Contact Tooth wheels 42, in case oil initially hinders the motion of gear train 42 when preventing that ram air turbine 20 from launching.The oil level of stowed position also is designed to be lower than the level of Sealing 70, to prevent from by mistake leaking and to prevent from can not operating as required when Sealing 70 leaks.
Outside axially compact, the housing main body 40 of gear-box 30 is compact at thickness also.For example, housing main body 40 is engaged in plane P 1And P 2In the radial envelope scope between (Fig. 3 A) so that about axis A all in the radial direction, housing main body 40 is less than 6 inches/15.24 centimetres.That is to say, even the bolt pattern that the second flange 48 has (bolt pattern) is also all in 6 inches/15.24 centimetres envelope scope.In addition, if surpassed 6 inches/15.24 centimetres envelope scope, the then extra sheathing material strength test of aircraft industry requirement.Exemplary materials for the manufacture of housing main body 40 is aluminum alloy, for example according to 6061 aluminium of AMS4027.According to the exploitation of metallic material character and the standardization (MMPDS) of having set aircraft industry material standard, only until 6 inches original material sizes just have S base character.The testing of materials of larger original material size has shown the reduction of fatigue property.Because housing main body satisfies 6 inches/15.24 centimetres envelope scope, so avoided the cost of extra test.Therefore, housing main body 40 comprises following feature: radially amplify section 40a, radial depressions section 40c and be in the oily filling channel 60 that overflows filling position (spill-to-fill location) about oil groove 56, all are encapsulated in plane P 1And P 2Between these 6 inches envelope scopes in.
With reference to Fig. 2 A and 2B, the second axial end portion 54 of housing main body 40 opens into the inner chamber 44 in the housing main body 40 usually, to be used for several functions.In one aspect, gear train 42 and other inner members can be installed in the inner chamber 44 by the second axial end portion 54.Next, the second axial end portion 54 serves as the access location of inner chamber 44 and serves as support so that the operation of test motor detecting gear-box 30.With regard to this point, the second axial end portion 54 comprises flange 54a, and flange 54a axially gives prominence to and comprises a plurality of attached exoncoma 54b, is used for testing motor and is fixed to housing main body 40.Flange 54a only partly circumferentially extends to avoid (clear) lid 80 around axis A.The weight that the flange 54a of this part has reduced gear-box 30 is with size envelope scope and prevent that gear-box 30 from contacting adjacent aircaft configuration.
Also with reference to Fig. 5, it shows the independent view of annular cover 80, and annular cover 80 comprises circumferential body 82, and circumferential body 82 is extended around central opening 84 and between the first axial side 86 and the second axial side 88.In this example, the second axial side 88 is towards interior, the inner chamber 44 in housing main body 40.Thereby the first axial side 86 towards outside, away from inner chamber 44.
Circumferential body 82 comprises antelabium 90, and antelabium 90 extends to free terminal 90a from the first axial side 86.Therefore, antelabium 90 defines the axial antelabium dimension D that is roughly parallel to axis A, and axis A also is the central axis of opening 84.Axially the antelabium dimension D is about changing around the circumferential position of axis A.Therefore, antelabium 90 has the first axial antelabium dimension D 1 and has less than axial the second axial antelabium dimension D 2 of antelabium dimension D 1 at the second circumferential position at the first circumferential position.In this example, antelabium 90 has relatively consistent axial antelabium dimension D with respect to the circumferential section of axis A from 8 o ' clock positions to 4 o ' clock positions.Then, axial antelabium dimension D little by little tapers to the minimum axial direction antelabium dimension D of 6 o ' clock positions.Therefore, 60% of the circumference of antelabium 90 residue 40% with consistent axial antelabium dimension D and circumference has the axial antelabium dimension D that reduces.The section of shown convergent also has contribution to useful guiding circumference, thereby has obtained about 75% useful guiding circumference.In other examples, the 50-90% of the circumference of antelabium 90 has consistent axial antelabium dimension D and remaining circumference has the axial antelabium dimension D that reduces.
The antelabium 90 of annular cover 80 serves as guide portion, is used for installation testing motor on the housing main body 40 of gear-box 30.When the installation testing motor, antelabium 90 is used for guiding test motor and will tests motor and aim at axis A.With regard to that, antelabium 90 does not need to have consistent axial antelabium size provides this function.In addition, antelabium 90 has also reduced the weight of gear-box 30 and size envelope scope to avoid adjacent aircaft configuration.RAT equipment has the tight envelope scope restriction from the gear-box end to the door usually, so this is useful feature.
Annular cover 80 also comprises anti-rotational feature 100.In this example, anti-rotational feature 100 comprises that first radially extends ear 100a and second and radially extend ear 100b.Radially extend ear 100a and 100b and usually depart from and reach about 180 °, but also alternately use other bias.Radially extend the flange 54a at the second axial end portion 54 places of ear 100a and 100b latch housing main body 40.Therefore, when annular cover 80 was assembled on the second axial end portion 54 of housing main body 40, annular cover 80 can not be around axis A rotation, because flange 54a serves as the rotation retainer.With regard to this point, when annular cover 80 is assembled in the gear-box 30, radially extend the suitable orientation that ear 100a and 100b and flange 54a have also guaranteed annular cover 80.Anti-rotational feature 100 is also resisted the rotating force of the moving member (for example bearing) in the gear-box 30.
Shown in Fig. 4 A, the second axial side 88 of annular cover 80 comprises that first extends axially wall 102 and second and extend axially that wall 104, the second extends axially wall 104 and the first axial walls 102 is radially spaced apart to limit the depression 106 between them.In this example, depression 106 is annular channels.At least a portion of depression 106 defines at least a portion of oil groove 56, so that when ram air turbine 20 was in stowed position, at least some in the oil were maintained in the depression 106.
Although show in the example shown the combination of feature, do not need they are all made up the benefit that realizes various embodiments of the present disclosure.In other words, needn't comprise arbitrary whole features shown in the drawings or all parts that schematically show in the accompanying drawings according to embodiment's designed system of the present disclosure.And, the selected feature of an exemplary embodiment can with the selected Feature Combination of other exemplary embodiments.
Being described in of front is illustrative rather than restrictive in essence.To those skilled in the art, the change of disclosed example and modification can become obviously, and it needn't depart from purport of the present disclosure.Can only determine to give legal protection scope of the present disclosure by the research claims.

Claims (20)

1. ram air turbine gearbox-case comprises:
Housing main body, described housing main body comprises the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane, described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately, described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part.
2. ram air turbine gearbox-case as claimed in claim 1, wherein, described oil groove comprises the raceway groove that partly circumferentially extends around described axis.
3. ram air turbine gearbox-case as claimed in claim 1, wherein, described housing main body comprises and the described adjacent radial depressions section of section that radially amplifies.
4. ram air turbine gearbox-case as claimed in claim 3, wherein, described radial depressions section is limited to the positive feature of extending in the described oil groove.
5. ram air turbine gearbox-case as claimed in claim 3, wherein, described radial depressions section is limited to the rib on the described housing main body.
6. ram air turbine gearbox-case as claimed in claim 1, wherein, described housing main body comprises oily filling channel, described oily filling channel extends between the open outlet in the open entrance in the place, outside of described housing main body and described oil groove place.
7. ram air turbine gearbox-case as claimed in claim 1, wherein, described housing main body in whole in the radial direction spans no longer than 6 inches/15.24 centimetres.
8. ram air turbine gearbox-case as claimed in claim 1, comprise the annular cover that is installed on described the second axial end portion, described annular cover comprises circumferential body, described circumferential body is extended between the first axial side and the second axial side around central opening and about the central axis of described opening, described circumferential body comprises antelabium, described antelabium extends to free terminal limiting axial antelabium size from described the first axial side, and described axial antelabium size is about around the circumferential position of described central axis and change.
9. ram air turbine gearbox-case as claimed in claim 8, wherein, described second axial side of described annular cover limits described oil groove at least in part.
10. ram air turbine gearbox-case as claimed in claim 9, wherein, described circumferential body comprises that in described the second axial side first extends axially wall and second and extend axially wall, and described second extends axially wall and described the first axial walls is radially spaced apart to limit the depression between them.
11. ram air turbine gearbox-case as claimed in claim 8, wherein, described circumferential body comprises that first radially extends ear and second and radially extend ear.
12. ram air turbine gearbox-case as claimed in claim 8, wherein, described antelabium circumferentially extends around described central axis, and the 50-90% of the circumference of described antelabium has consistent axial antelabium size and remaining circumference has the axial antelabium size that reduces.
13. a ram air turbine gear-box comprises:
Housing main body, described housing main body comprises the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane, described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately, described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part;
At least one gear, described at least one gear is installed in the described housing main body; With
Lid, described lid is installed in described the second axial end portion place, described lid comprises circumferential body, described circumferential body is extended around central opening and between the first axial side and the second axial side, described circumferential body comprises antelabium, described antelabium extends to free terminal limiting axial antelabium size from described the first axial side, and described axial antelabium size is about around the circumferential position of described central axis and change.
14. ram air turbine gear-box as claimed in claim 13, wherein, described housing main body comprises oily filling channel, and described oily filling channel extends between the open outlet in the open entrance in place, the outside of described housing main body and described oil groove place.
15. a ram air turbine comprises:
The generator section;
The turbo machine section, described turbo machine section can move between expanded position and stowed position; With
Gear-box, described gear-box is connected to described turbo machine section, so that described turbo machine section can operate to drive described generator section by described gear-box, described gear-box comprises housing main body, described housing main body comprises the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane, described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately, described housing main body comprises and radially amplifies section, the described oil groove that radially amplifies in the described inner chamber that section limits described housing main body at least in part.
16. ram air turbine as claimed in claim 15, wherein, described housing main body comprises oily filling channel, and described oily filling channel extends between the open outlet in the open entrance in place, the outside of described housing main body and described oil groove place.
17. ram air turbine as claimed in claim 16, wherein, at described stowed position, described oily filling channel is located so that the oil in described oil groove contacts before described at least one gear, and the oil in the described oil groove will overflow from described oily filling channel.
18. one kind is installed in method on the ram air turbine with gear-box, described method comprises:
Gear-box is provided, described gear-box comprises housing main body, described housing main body comprises the first flange and the second flange, described the first flange limit the first plane, described the second flange limit the second plane, described the second flat transverse is in described the first plane, described housing main body is around Axis Extension and have the first axial end portion and the second relative axial end portion, described the first axial end portion and described the second axial end portion open into the inner chamber of described housing main body separately, described housing main body comprises and radially amplifies section, the oil groove in the described inner chamber of the described housing main body of described radially amplification region paragraph qualification;
Described housing main body is fixed to the turbo machine section; And
Described the second flange is fixed in pillar and the generator section at least one.
19. method as claimed in claim 18, comprise lid is fixed on described the second axial end portion, described lid comprises circumferential body, described circumferential body is extended between the first axial side and the second axial side around central opening and about the central axis of described opening, described circumferential body comprises antelabium, described antelabium extends to free terminal limiting axial antelabium size from described the first axial side, and described axial antelabium size is about around the circumferential position of described central axis and change.
20. method as claimed in claim 18 comprises described housing main body is provided as to have all in the radial direction no longer than 6 inches/15.24 centimetres span, to avoid the strength test of industry requirement.
CN201310101472.1A 2012-03-27 2013-03-27 For the compact gear of ram air turbine oil management Active CN103363067B (en)

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Application Number Priority Date Filing Date Title
US13/430890 2012-03-27
US13/430,890 2012-03-27
US13/430,890 US9115799B2 (en) 2012-03-27 2012-03-27 Compact gearbox for ram air turbine oil management

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CN103363067A true CN103363067A (en) 2013-10-23
CN103363067B CN103363067B (en) 2016-03-16

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